EP3794219B1 - Agencements d'aube et d'enveloppe pour une turbomachine - Google Patents

Agencements d'aube et d'enveloppe pour une turbomachine Download PDF

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Publication number
EP3794219B1
EP3794219B1 EP19727452.5A EP19727452A EP3794219B1 EP 3794219 B1 EP3794219 B1 EP 3794219B1 EP 19727452 A EP19727452 A EP 19727452A EP 3794219 B1 EP3794219 B1 EP 3794219B1
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EP
European Patent Office
Prior art keywords
vane
slot
surface portion
leading
trailing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19727452.5A
Other languages
German (de)
English (en)
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EP3794219A1 (fr
Inventor
Christopher J SHAW
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cummins Ltd
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Cummins Ltd
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Publication date
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Publication of EP3794219A1 publication Critical patent/EP3794219A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • a pneumatically or hydraulically operated actuator 16 is operable to control the axial position of the nozzle ring 5 within an annular cavity 19 defined by a portion 26 of the turbine housing via an actuator output shaft (not shown), which is linked to a stirrup member (not shown).
  • the stirrup member in turn engages axially extending guide rods (not shown) that support the nozzle ring 5. Accordingly, by appropriate control of the actuator 16 the axial position of the guide rods and thus of the nozzle ring 5 can be controlled.
  • electrically operated actuators could be used in place of a pneumatically or hydraulically operated actuator 16.
  • the vane inner surface further including a trailing surface portion extending along at least 33% of the median line and, which, at room temperature and when the leading surface portions are in contact, is spaced from an opposed trailing surface portion of the slot surface by a distance in the range 10 microns to 250 microns, and more preferably at least 25 microns and/or no more than 100 microns.
  • the turbine may include a rotational mechanism for generating a rotational torque for urging the nozzle ring to rotate with respect to the shroud, in a sense which urges the respective leading surface portions of the vanes and slots together.
  • this rotational mechanism is simply the force exerted by the exhaust gas on the vanes.
  • Fig. 3 is a view looking towards the shroud 6 from the nozzle ring 5 (i.e. towards the right side of Fig. 1 ).
  • the shroud defines slots 30 (that is, through-holes) for receiving respective ones of the vanes 7.
  • the edge of each slot is an inwardly-facing slot lateral (i.e. transverse to the axis 100) slot surface. Note that in Fig. 3 the slots 30 are not illustrated as having the same profile as the vanes 7 of Fig. 2 , but typically the respective profiles do have substantially the same shape although the slots are of greater size than the vanes.
  • Fig. 4 is another view looking in the axial direction from the nozzle ring 5 towards the shroud 6 (i.e. towards the right side of Fig. 1(a) ), showing a representative vane 7 inserted into a respective representative slot 30.
  • the vane 7 has a generally arcuate (crescent-shaped) profile, although in other forms the vanes are substantially planar.
  • Fig. 6 and 7 illustrate the formation of foreign object damage (FOD) during the use of the turbine of Fig. 5 .
  • the large arrow indicates the general direction of rotation of the exhaust gas entering the turbine, and rotation of the turbine wheel.
  • Fig. 6 is a view of the shroud in the axial direction
  • Fig. 7 is an enlarged portion of Fig. 6 .
  • the shroud defines the slots 130 which contain the respective vanes 107. It has been found experimentally that for a given one of the vanes 107 (indicated as 107a) a line 150 exists, extending from the trailing edge of the adjacent vane (indicated as 107b) in the upstream direction (i.e.
  • the spacing between the vane inner surface 241 and the slot inner surface 246 in the trailing surface portion 266 has the further advantage of reducing the risk of the vane 207 becoming stuck to the shroud due to a thermal transient.
  • the contact point 3463 may be on a line 3464 which is a tangent to the profile of the vane 307 and passes through the rotational axis 100, which is at the centre of the shroud. This position is chosen to minimise (or substantially eliminate) radial force transmitted between the vane and the shroud.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Claims (10)

  1. Turbine comprenant :
    (i) une roue de turbine (9) ayant un axe (100),
    (ii) un carter de turbine (1) pour définir une chambre pour recevoir la roue de turbine pour une rotation de la roue de turbine autour de l'axe, le carter de turbine définissant en outre une entrée de gaz, et un passage d'entrée annulaire à partir de l'entrée de gaz jusqu'à la chambre,
    (iii) un carénage de forme annulaire (6) définissant une pluralité de fentes (230 ; 330) et encerclant l'axe, chaque fente ayant une surface de fente ; et
    (iv) aube de distribution (5) supportant une pluralité d'aubes (207 ; 307) qui s'étendent à partir de l'aube de distribution parallèlement à l'axe, et se projettent à travers des fentes respectives ;
    chacune des aubes comportant :
    une surface d'aube s'étendant axialement qui inclut (i) une surface extérieure d'aube faisant face à une surface radialement extérieure de la fente correspondante, (ii) une surface intérieure d'aube opposée (241) faisant face à une surface radialement intérieure (246) de la fente correspondante, et
    une ligne médiane entre la surface intérieure d'aube et la surface extérieure d'aube s'étendant depuis une extrémité d'attaque de l'aube jusqu'à une extrémité de fuite de l'aube ;
    caractérisée en ce que :
    l'aube est positionnable avec une partie de surface d'attaque (260 ; 368) de la surface intérieure d'aube (241 ; 341) en contact avec une partie de surface d'attaque correspondante (2461 ; 3462) de la surface de fente respective (246) ;
    la surface intérieure d'aube (241) incluant en outre une partie de surface de fuite (266 ; 366) s'étendant le long d'au moins 33 % de la ligne médiane, et qui, à température ambiante et lorsque les parties de surface d'attaque sont en contact, est espacée d'une partie de surface de fuite opposée (2462 ; 3461) de la surface de fente (246) d'une distance comprise dans la plage allant de 10 microns à 250 microns.
  2. Turbine selon la revendication 1, dans laquelle, à température ambiante et lorsque les parties de surface d'attaque sont en contact, les parties de surface de fuite (266 ; 366) sont espacées d'une distance comprise dans la plage allant de 25 microns à 100 microns.
  3. Turbine selon la revendication 1 ou la revendication 2, dans laquelle la partie de surface de fuite (266 ; 366) de la surface d'aube s'étend sur au moins 50 %, de manière plus préférée au moins 60%, au moins 70 % ou au moins 80 % de la longueur de la ligne médiane.
  4. Turbine selon la revendication 1, la revendication 2 ou la revendication 3 dans laquelle la partie de surface d'attaque (260 ; 368) de la surface d'aube s'étend le long d'au moins 15 % de la longueur de la ligne médiane, les profils respectifs de la partie de surface d'attaque de la surface d'aube et d'une partie de surface d'attaque correspondante de la surface de fente respective divergeant l'un de l'autre de pas plus de 1 micron à 50 microns, ou de préférence de 1 micron à 25 microns.
  5. Turbine selon la revendication 4, dans laquelle la partie de surface d'attaque de la surface d'aube inclut un point où la ligne médiane entrecroise le bord d'attaque de l'aube.
  6. Turbine selon la revendication 1, la revendication 2 ou la revendication 3, dans laquelle la partie de surface d'attaque de la surface d'aube s'étend le long de moins de 5 % de la longueur de la ligne médiane.
  7. Turbine selon l'une quelconque des revendications précédentes, dans laquelle, lors de l'utilisation, des parties radialement intérieures des surfaces de l'aube et de la fente sont à une pression inférieure à des parties radialement extérieures des surfaces de l'aube et de la fente.
  8. Turbine selon l'une quelconque des revendications précédentes, dans laquelle une partie de surface de fuite (266 ; 366) de la surface d'aube est espacée d'une partie de surface de fuite opposée (2462 ; 3461) de la surface de fente (246) d'une distance qui est constante le long de la partie de surface de fuite.
  9. Turbine selon l'une quelconque des revendications précédentes, dans laquelle une région de transition (2463) est fournie entre la partie de surface d'attaque (2461) de la surface de fente respective (246) et la partie de surface de fuite (2462) de la surface de fente, la région de transition incluant une partie convexe (2464) à proximité de la partie de surface d'attaque et une partie concave (2465) à proximité de la partie de surface de fuite.
  10. Turbocompresseur comprenant une turbine selon l'une quelconque des revendications précédentes.
EP19727452.5A 2018-05-15 2019-05-14 Agencements d'aube et d'enveloppe pour une turbomachine Active EP3794219B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1807883.2A GB2574195B (en) 2018-05-15 2018-05-15 Vane and shroud arrangements for a turbo-machine
PCT/GB2019/051316 WO2019220096A1 (fr) 2018-05-15 2019-05-14 Agencements d'aube et d'enveloppe pour une turbomachine

Publications (2)

Publication Number Publication Date
EP3794219A1 EP3794219A1 (fr) 2021-03-24
EP3794219B1 true EP3794219B1 (fr) 2023-09-06

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19727452.5A Active EP3794219B1 (fr) 2018-05-15 2019-05-14 Agencements d'aube et d'enveloppe pour une turbomachine

Country Status (5)

Country Link
US (1) US11434779B2 (fr)
EP (1) EP3794219B1 (fr)
CN (1) CN112424449B (fr)
GB (1) GB2574195B (fr)
WO (1) WO2019220096A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11319832B2 (en) * 2020-02-27 2022-05-03 Rolls-Royce North American Technologies Inc. Single movement convergent and convergent-divergent nozzle

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3542031A1 (fr) * 2016-11-15 2019-09-25 Cummins Ltd Agencement d'aubes pour turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5452986A (en) * 1994-01-12 1995-09-26 Dresser-Rand Company Vaned diffuser
AU2000267060A1 (en) * 2000-07-19 2002-01-30 Alliedsignal Turbo S.A. Sliding vane turbocharger with graduated vanes
KR20080021119A (ko) * 2005-06-07 2008-03-06 커민스 터보 테크놀러지스 리미티드 가변구조 터빈
GB0804780D0 (en) * 2008-03-14 2008-04-16 Cummins Turbo Tech Ltd A variable geometry turbine
GB2462115A (en) * 2008-07-25 2010-01-27 Cummins Turbo Tech Ltd Variable geometry turbine
GB0822474D0 (en) * 2008-12-10 2009-01-14 Cummins Turbo Tech Ltd Variable geometry turbine nozzle ring
GB0921350D0 (en) * 2009-12-05 2010-01-20 Cummins Turbo Tech Ltd Vaariable geometry turbomachine
GB2497786B (en) * 2011-12-21 2016-09-07 Cummins Ltd Variable geometry turbine having vane slots with portions of increased clearance
DE102013002192A1 (de) * 2013-02-07 2014-08-07 Daimler Ag Turbine für einen Abgasturbolader
CN104937234A (zh) * 2013-02-21 2015-09-23 三菱重工业株式会社 可变容量式排气涡轮增压机

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3542031A1 (fr) * 2016-11-15 2019-09-25 Cummins Ltd Agencement d'aubes pour turbomachine

Also Published As

Publication number Publication date
EP3794219A1 (fr) 2021-03-24
US11434779B2 (en) 2022-09-06
GB201807883D0 (en) 2018-06-27
WO2019220096A1 (fr) 2019-11-21
GB2574195B (en) 2022-06-08
CN112424449B (zh) 2023-05-30
CN112424449A (zh) 2021-02-26
GB2574195A (en) 2019-12-04
US20210222582A1 (en) 2021-07-22

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